The report 'Resurrected DSCOVR Propulsion System – Challenges and Lessons Learned' contains a schematic of the propulsion system:

and indicates thruster locations:

thruster 9 and 10 are on the bottom:

The thrusters were used as follows:

... the DSCOVR propulsion system, which utilizes ten 4.5 N thrusters in blowdown mode to perform Midcourse Correction (MCC) maneuvers, Lissajous Orbit Insertion (LOI) at Lagrangian point L1, momentum unloading maneuvers, and station keeping delta-v maneuvers at L1.

The first planned thruster maneuver was the MCC burn, which was designed to correct any launch dispersion in the spacecraft trajectory. ... The MCC #1 maneuver was actually performed using Thrusters 9 and 10 for +Z delta-V direction and Thrusters 1 through 8 for attitude control.

On June 7, 2015 (115 days after launch), the Lissajous Orbit Insertion (LOI) burn placed DSCOVR in orbit at the Sun-Earth L1 Lagrangian point. The burn consisted of two segments: one burn approximately 4 hours long (152.4 m/s) and a second burn approximately 35 minutes long (13.9 m/s). The burn was performed in two segments so the Flight Dynamics team could re-calibrate the second segment based on the information from the first segment. The thruster configuration used Thrusters 9 and 10 for +Z delta-V and the Thrusters 1 through 8 as needed for attitude control.

The report 'Resurrected DSCOVR Propulsion System – Challenges and Lessons Learned' contains a schematic of the propulsion system:

and indicates thruster locations:

thruster 9 and 10 are on the bottom:

The thrusters were used as follows:

... the DSCOVR propulsion system, which utilizes ten 4.5 N thrusters in blowdown mode to perform Midcourse Correction (MCC) maneuvers, Lissajous Orbit Insertion (LOI) at Lagrangian point L1, momentum unloading maneuvers, and station keeping delta-v maneuvers at L1.

The first planned thruster maneuver was the MCC burn, which was designed to correct any launch dispersion in the spacecraft trajectory. ... The MCC #1 maneuver was actually performed using Thrusters 9 and 10 for +Z delta-V direction and Thrusters 1 through 8 for attitude control.

On June 7, 2015 (115 days after launch), the Lissajous Orbit Insertion (LOI) burn placed DSCOVR in orbit at the Sun-Earth L1 Lagrangian point. The burn consisted of two segments: one burn approximately 4 hours long (152.4 m/s) and a second burn approximately 35 minutes long (13.9 m/s). The burn was performed in two segments so the Flight Dynamics team could re-calibrate the second segment based on the information from the first segment. The thruster configuration used Thrusters 9 and 10 for +Z delta-V and the Thrusters 1 through 8 as needed for attitude control.

The report 'Resurrected DSCOVR Propulsion System – Challenges and Lessons Learned' contains a schematic of the propulsion system:

and indicates thruster locations:

The report 'Resurrected DSCOVR Propulsion System – Challenges and Lessons Learned' contains a schematic of the propulsion system:

and indicates thruster locations:

thruster 9 and 10 are on the bottom:

The thrusters were used as follows:

... the DSCOVR propulsion system, which utilizes ten 4.5 N thrusters in blowdown mode to perform Midcourse Correction (MCC) maneuvers, Lissajous Orbit Insertion (LOI) at Lagrangian point L1, momentum unloading maneuvers, and station keeping delta-v maneuvers at L1.

The first planned thruster maneuver was the MCC burn, which was designed to correct any launch dispersion in the spacecraft trajectory. ... The MCC #1 maneuver was actually performed using Thrusters 9 and 10 for +Z delta-V direction and Thrusters 1 through 8 for attitude control.

On June 7, 2015 (115 days after launch), the Lissajous Orbit Insertion (LOI) burn placed DSCOVR in orbit at the Sun-Earth L1 Lagrangian point. The burn consisted of two segments: one burn approximately 4 hours long (152.4 m/s) and a second burn approximately 35 minutes long (13.9 m/s). The burn was performed in two segments so the Flight Dynamics team could re-calibrate the second segment based on the information from the first segment. The thruster configuration used Thrusters 9 and 10 for +Z delta-V and the Thrusters 1 through 8 as needed for attitude control.